US20100183811A1 - METHOD FOR ADJUSTING THE NUMBER OF PHASES OF A PTAl-LAYER OF A GAS TURBINE COMPONENT AND METHOD FOR PRODUCING A SINGLE-PHASE PTAl-LAYER ON A GAS TURBINE COMPONENT - Google Patents
METHOD FOR ADJUSTING THE NUMBER OF PHASES OF A PTAl-LAYER OF A GAS TURBINE COMPONENT AND METHOD FOR PRODUCING A SINGLE-PHASE PTAl-LAYER ON A GAS TURBINE COMPONENT Download PDFInfo
- Publication number
- US20100183811A1 US20100183811A1 US12/602,427 US60242708A US2010183811A1 US 20100183811 A1 US20100183811 A1 US 20100183811A1 US 60242708 A US60242708 A US 60242708A US 2010183811 A1 US2010183811 A1 US 2010183811A1
- Authority
- US
- United States
- Prior art keywords
- layer
- gas turbine
- turbine component
- ptal
- produce
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 title claims description 10
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 2
- 238000000265 homogenisation Methods 0.000 claims abstract description 17
- 239000000463 material Substances 0.000 claims abstract description 10
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Substances [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 23
- 229910052697 platinum Inorganic materials 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 239000012190 activator Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000009713 electroplating Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000005240 physical vapour deposition Methods 0.000 description 1
- 238000004544 sputter deposition Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/02—Pretreatment of the material to be coated
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/06—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases
- C23C10/16—Solid state diffusion of only metal elements or silicon into metallic material surfaces using gases more than one element being diffused in more than one step
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
- C23C10/34—Embedding in a powder mixture, i.e. pack cementation
- C23C10/58—Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than one step
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/60—After-treatment
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
Definitions
- the invention relates to a method for adjusting the number of phases of a PtAl layer of a gas turbine component, in particular a component of an aircraft engine, as well as a method for producing a single-phase PtAl layer on a gas turbine component.
- Single-phase PtAl layers are already known just like two-phase PtAl layers.
- For single-phase PtAl layers most of the time homogenization is required after aluminization in order to lower the Al and Pt concentrations enough that a single-phase structure emerges.
- This structure has advantages with respect to its mechanical properties.
- the objective of the invention is creating a possibility for producing a single-phase PtAl layer in a simple and cost-effective manner. Furthermore, it would be particularly desirable if a possibility could be produced for influencing or adjusting the phase-ness of a PtAl layer.
- a method for influencing, in particular adjusting, the number of phases of a PtAl layer of a gas turbine component, in particular of a component of an aircraft engine is provided, which is carried out or supposed to be carried out in particular when producing the type of layer during the course of the production or reconditioning of the type of gas turbine raw part.
- steps assigned to a first group are carried out to produce a single-phase PtAl layer on the gas turbine component, and steps assigned to a second group are carried out to produce a two-phase PtAl layer on a gas turbine component.
- the steps in the first group include the following steps: application of a Pt layer to the gas turbine component, the thickness thereof being less than 4 ⁇ m; homogenization such that the platinum (Pt) in the base material of the gas turbine component is diffused; and aluminization and control such that an aluminum content (Al content) that is less than or equal to 23% by weight is adjusted, preferably less than or equal to 22% by weight, preferably less than or equal to 20% by weight, preferably less than or equal to 18% by weight, preferably less than or equal to 15% by weight, preferably less than or equal to 13% by weight, preferably less than or equal to 10% by weight.
- Al content aluminum content
- the following steps are part of the second group: application of a platinum layer (Pt layer) to the gas turbine component, the thickness thereof being in the range of 5 ⁇ m to 8 ⁇ m, preferably in the range of 5 ⁇ m to 6 ⁇ m; homogenization such that the platinum in the base material of the gas turbine component is diffused; and aluminization in order to produce the PtAl layer.
- Pt layer platinum layer
- the aluminization to produce a two-phase PtAl layer on the gas turbine component is carried out in a preferred embodiment over a period of time that lies in the range of 8 to 15 hours, preferably in the range of 11 to 13 hours.
- a method for producing a single-phase PtAl layer on a gas turbine component in particular for a component of an aircraft engine, is provided. This method is carried out in particular during the course of the production or reconditioning of the type of gas turbine components.
- the method features the following steps: application of a Pt layer to the gas turbine component, the thickness thereof being less than 4 ⁇ m; homogenization such that the platinum in the base material of the gas turbine component is diffused; and aluminization to produce the PtAl layer and control such that an Al content that is less than or equal to 23% by weight is adjusted, preferably less than or equal to 22% by weight, preferably less than or equal to 20% by weight, preferably less than or equal to 18% by weight, preferably less than or equal to 15% by weight, preferably less than or equal to 13% by weight, preferably less than or equal to 10% by weight.
- platinum layer which is applied to this gas turbine component to produce a single-phase PtAl layer on the gas turbine component, is applied with a thickness that is in the range of 1 to 2 ⁇ m.
- An advantageous embodiment provides that the homogenization, which is carried out to produce a single-phase PtAl layer on the gas turbine component, in order to cause the platinum in the base material of the gas turbine component to diffuse, is carried out over a period of time that lies in the range of 0.2 to 4 hours, preferably in the range of 0.5 to 2 hours.
- a particularly preferred further development provides for the aluminization to produce a single-phase PtAl layer on the gas turbine component to be carried out of over a period of time that lies in the range of 3 to 11 hours, in particular in the range of 6 to 10 hours.
- the base material of the gas turbine component may be a nickel-based alloy or a cobalt-based alloy for example.
- the aluminization for producing the single-phase and/or two-phase PtAl for example may be carried out by CVD, e.g., in a gas phase or in a pack cementation process.
- the Pt layer can be applied for example by electroplating or by sputtering.
- the application of the Pt layer is carried out by PVD or by CVD.
- the Pt layer then be homogenized as usual.
- This homogenization may be of a relatively short duration (e.g., 0.5 to 2 hours).
- aluminization is applied in an advantageous embodiment.
- This aluminization can be controlled such that it yields a low aluminum content such as, for example, an aluminum content of less than 20% or of less than 20% by weight or of less than 22% or of less than 22% by weight.
- the invention makes possible, at least in the advantageous further development, production with low manufacturing costs, because the customary platinum layer thickness of 4 to 6 ⁇ m can be reduced to approx. 1 to 2 ⁇ m, because it is possible to dispense with a homogenization that is to be carried out after the aluminization, something that applies in particular for single-phase PtAl layer.
Abstract
A method for adjusting the number of phases of a PtAl layer of a component of an aircraft engine is disclosed. In an embodiment, the following steps produce a single-phase PtAl layer on the gas turbine component: application of a Pt layer to the gas turbine component, the thickness thereof being less than 4 μm; homogenization such that the Pt in the base material of the gas turbine component is diffused; and aluminization and control such that an Al content that is less than or equal to 23% by weight is adjusted; and the following steps produce a two-phase PtAl layer: application of a Pt layer to the gas turbine component, the thickness thereof being in the range of 5 μm to 8 μm; homogenization such that the Pt in the base material of the gas turbine component is diffused; and aluminization in order to produce the PtAl layer.
Description
- This application claims the priority of International Application No. PCT/DE2008/000839, filed May 15, 2008, and German Patent Document No. 10 2007 025 697.5, filed Jun. 1, 2007, the disclosures of which are expressly incorporated by reference herein.
- The invention relates to a method for adjusting the number of phases of a PtAl layer of a gas turbine component, in particular a component of an aircraft engine, as well as a method for producing a single-phase PtAl layer on a gas turbine component.
- Single-phase PtAl layers are already known just like two-phase PtAl layers. For single-phase PtAl layers, most of the time homogenization is required after aluminization in order to lower the Al and Pt concentrations enough that a single-phase structure emerges. This structure has advantages with respect to its mechanical properties. With this as the background, the objective of the invention is creating a possibility for producing a single-phase PtAl layer in a simple and cost-effective manner. Furthermore, it would be particularly desirable if a possibility could be produced for influencing or adjusting the phase-ness of a PtAl layer.
- Thus, in particular a method for influencing, in particular adjusting, the number of phases of a PtAl layer of a gas turbine component, in particular of a component of an aircraft engine, is provided, which is carried out or supposed to be carried out in particular when producing the type of layer during the course of the production or reconditioning of the type of gas turbine raw part. In this case, it is provided that steps assigned to a first group are carried out to produce a single-phase PtAl layer on the gas turbine component, and steps assigned to a second group are carried out to produce a two-phase PtAl layer on a gas turbine component. The steps in the first group include the following steps: application of a Pt layer to the gas turbine component, the thickness thereof being less than 4 μm; homogenization such that the platinum (Pt) in the base material of the gas turbine component is diffused; and aluminization and control such that an aluminum content (Al content) that is less than or equal to 23% by weight is adjusted, preferably less than or equal to 22% by weight, preferably less than or equal to 20% by weight, preferably less than or equal to 18% by weight, preferably less than or equal to 15% by weight, preferably less than or equal to 13% by weight, preferably less than or equal to 10% by weight.
- The following steps are part of the second group: application of a platinum layer (Pt layer) to the gas turbine component, the thickness thereof being in the range of 5 μm to 8 μm, preferably in the range of 5 μm to 6 μm; homogenization such that the platinum in the base material of the gas turbine component is diffused; and aluminization in order to produce the PtAl layer.
- The aluminization to produce a two-phase PtAl layer on the gas turbine component is carried out in a preferred embodiment over a period of time that lies in the range of 8 to 15 hours, preferably in the range of 11 to 13 hours.
- Furthermore, a method for producing a single-phase PtAl layer on a gas turbine component, in particular for a component of an aircraft engine, is provided. This method is carried out in particular during the course of the production or reconditioning of the type of gas turbine components. The method features the following steps: application of a Pt layer to the gas turbine component, the thickness thereof being less than 4 μm; homogenization such that the platinum in the base material of the gas turbine component is diffused; and aluminization to produce the PtAl layer and control such that an Al content that is less than or equal to 23% by weight is adjusted, preferably less than or equal to 22% by weight, preferably less than or equal to 20% by weight, preferably less than or equal to 18% by weight, preferably less than or equal to 15% by weight, preferably less than or equal to 13% by weight, preferably less than or equal to 10% by weight.
- An advantageous further development provides that the platinum layer, which is applied to this gas turbine component to produce a single-phase PtAl layer on the gas turbine component, is applied with a thickness that is in the range of 1 to 2 μm.
- An advantageous embodiment provides that the homogenization, which is carried out to produce a single-phase PtAl layer on the gas turbine component, in order to cause the platinum in the base material of the gas turbine component to diffuse, is carried out over a period of time that lies in the range of 0.2 to 4 hours, preferably in the range of 0.5 to 2 hours.
- A particularly preferred further development provides for the aluminization to produce a single-phase PtAl layer on the gas turbine component to be carried out of over a period of time that lies in the range of 3 to 11 hours, in particular in the range of 6 to 10 hours.
- It is thus especially preferred that a very thin Pt layer, approx. 1 to 2 μm thick, be applied.
- The base material of the gas turbine component may be a nickel-based alloy or a cobalt-based alloy for example.
- The aluminization for producing the single-phase and/or two-phase PtAl for example may be carried out by CVD, e.g., in a gas phase or in a pack cementation process.
- It should be noted that the Pt layer can be applied for example by electroplating or by sputtering.
- In particular it can also be provided that the application of the Pt layer is carried out by PVD or by CVD.
- In particular it is provided that the Pt layer then be homogenized as usual. This homogenization may be of a relatively short duration (e.g., 0.5 to 2 hours). Afterwards, aluminization is applied in an advantageous embodiment. This aluminization can be controlled such that it yields a low aluminum content such as, for example, an aluminum content of less than 20% or of less than 20% by weight or of less than 22% or of less than 22% by weight. This means in particular that the donor and the activator are adjusted correspondingly.
- The invention makes possible, at least in the advantageous further development, production with low manufacturing costs, because the customary platinum layer thickness of 4 to 6 μm can be reduced to approx. 1 to 2 μm, because it is possible to dispense with a homogenization that is to be carried out after the aluminization, something that applies in particular for single-phase PtAl layer.
Claims (13)
1.-7. (canceled)
8. A method for adjusting a number of phases of a PtAl layer of a gas turbine component when producing the layer during a course of production or reconditioning of the gas turbine component:
comprising the steps of:
application of a Pt layer to the gas turbine component, a thickness of the Pt layer being less than 4 μm;
homogenization such that Pt in a base material of the gas turbine component is diffused; and
aluminization and control after the homogenization such that an Al content that is less than or equal to 23% by weight is adjusted;
to produce a single-phase PtAl layer on the gas turbine component;
and comprising the steps of:
application of a Pt layer to the gas turbine component, a thickness of the Pt layer being in a range of 5 μm to 8 μm;
homogenization such that Pt in a base material of the gas turbine component is diffused; and
aluminization after the homogenization in order to produce the PtAl layer;
to produce a two-phase PtAl layer on the gas turbine component.
9. The method according to claim 8 , wherein to produce the two-phase PtAl layer on the gas turbine component the thickness of the Pt layer is in a range of 5 μm to 6 μm.
10. The method according to claim 8 , wherein to produce the two-phase PtAl layer on the gas turbine component the aluminization is carried out of over a period of time that lies in the range of 8 to 15 hours.
11. A method for producing a single-phase PtAl layer on a gas turbine component during a course of production or reconditioning of the gas turbine component, comprising the steps of:
application of a Pt layer to the gas turbine component, a thickness of the Pt layer being less than 4 μm;
homogenization such that Pt in a base material of the gas turbine component is diffused; and
aluminization after the homogenization to produce the PtAl layer and control such that an Al content that is less than or equal to 23% by weight is adjusted.
12. The method according to claim 8 , wherein to produce the single-phase PtAl layer on the gas turbine component the Pt layer is applied with a thickness that is in the range of 1 μm to 2 μm.
13. The method according to claim 8 , wherein to produce the single-phase PtAl layer on the gas turbine component the homogenization is carried out over a period of time that lies in the range of 0.2 to 4 hours.
14. The method according to claim 8 , wherein to produce the single-phase PtAl layer on the gas turbine component the aluminization is carried out of over a period of time that lies in the range of 3 to 11 hours.
15. The method according to claim 8 , wherein the gas turbine component is a component of an aircraft engine.
16. The method according to claim 11 , wherein to produce the single-phase PtAl layer on the gas turbine component the Pt layer is applied with a thickness that is in the range of 1 μm to 2 μm.
17. The method according to claim 11 , wherein to produce the single-phase PtAl layer on the gas turbine component the homogenization is carried out over a period of time that lies in the range of 0.2 to 4 hours.
18. The method according to claim 11 , wherein to produce the single-phase PtAl layer on the gas turbine component the aluminization is carried out of over a period of time that lies in the range of 3 to 11 hours.
19. The method according to claim 11 , wherein the gas turbine component is a component of an aircraft engine.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007025697.5 | 2007-06-01 | ||
DE102007025697A DE102007025697A1 (en) | 2007-06-01 | 2007-06-01 | A method of adjusting the number of phases of a PtAl layer of a gas turbine engine component and methods of producing a single-phase PtAl film on a gas turbine engine component |
PCT/DE2008/000839 WO2008145093A2 (en) | 2007-06-01 | 2008-05-15 | Method for adjusting the number of phases of a pta1-layer of a gas turbine component and method for producing a single-phase pta1-layer on a gas turbine component |
Publications (1)
Publication Number | Publication Date |
---|---|
US20100183811A1 true US20100183811A1 (en) | 2010-07-22 |
Family
ID=39680926
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/602,427 Abandoned US20100183811A1 (en) | 2007-06-01 | 2008-05-15 | METHOD FOR ADJUSTING THE NUMBER OF PHASES OF A PTAl-LAYER OF A GAS TURBINE COMPONENT AND METHOD FOR PRODUCING A SINGLE-PHASE PTAl-LAYER ON A GAS TURBINE COMPONENT |
Country Status (4)
Country | Link |
---|---|
US (1) | US20100183811A1 (en) |
EP (1) | EP2150631A2 (en) |
DE (1) | DE102007025697A1 (en) |
WO (1) | WO2008145093A2 (en) |
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US6383306B1 (en) * | 2000-02-28 | 2002-05-07 | General Electric Company | Preparation of a nickel-base superalloy article having a decarburized coating containing aluminum and a reactive element |
US20020055004A1 (en) * | 1992-10-13 | 2002-05-09 | Walston William S. | Low-sulfur article having a platinum-aluminide protective layer, and its preparation |
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US6605364B1 (en) * | 2000-07-18 | 2003-08-12 | General Electric Company | Coating article and method for repairing a coated surface |
US20050260346A1 (en) * | 2004-03-16 | 2005-11-24 | General Electric Company | Method for aluminide coating a hollow article |
US20070122647A1 (en) * | 2005-11-28 | 2007-05-31 | Russo Vincent J | Duplex gas phase coating |
US20070134418A1 (en) * | 2005-12-14 | 2007-06-14 | General Electric Company | Method for depositing an aluminum-containing layer onto an article |
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US6066405A (en) * | 1995-12-22 | 2000-05-23 | General Electric Company | Nickel-base superalloy having an optimized platinum-aluminide coating |
US5897966A (en) * | 1996-02-26 | 1999-04-27 | General Electric Company | High temperature alloy article with a discrete protective coating and method for making |
-
2007
- 2007-06-01 DE DE102007025697A patent/DE102007025697A1/en not_active Withdrawn
-
2008
- 2008-05-15 US US12/602,427 patent/US20100183811A1/en not_active Abandoned
- 2008-05-15 EP EP08773258A patent/EP2150631A2/en not_active Withdrawn
- 2008-05-15 WO PCT/DE2008/000839 patent/WO2008145093A2/en active Application Filing
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US20020055004A1 (en) * | 1992-10-13 | 2002-05-09 | Walston William S. | Low-sulfur article having a platinum-aluminide protective layer, and its preparation |
US20010004474A1 (en) * | 1999-12-20 | 2001-06-21 | United Technologies Corporation | Methods of providing article with corrosion resistant coating and coated article |
US6383306B1 (en) * | 2000-02-28 | 2002-05-07 | General Electric Company | Preparation of a nickel-base superalloy article having a decarburized coating containing aluminum and a reactive element |
US6372321B1 (en) * | 2000-03-17 | 2002-04-16 | General Electric Company | Coated article with internal stabilizing portion and method for making |
US6605364B1 (en) * | 2000-07-18 | 2003-08-12 | General Electric Company | Coating article and method for repairing a coated surface |
US20030044633A1 (en) * | 2001-08-16 | 2003-03-06 | Nagaraj Bangalore Aswatha | Article having an improved platinum-aluminum-hafnium protective coating |
US20030116237A1 (en) * | 2001-12-20 | 2003-06-26 | Worthing Richard Roy | Process for rejuvenating a diffusion aluminide coating |
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US20080166589A1 (en) * | 2005-08-02 | 2008-07-10 | Mtu Aero Engines Gmbh | Component having a coating |
US20070122647A1 (en) * | 2005-11-28 | 2007-05-31 | Russo Vincent J | Duplex gas phase coating |
US20070134418A1 (en) * | 2005-12-14 | 2007-06-14 | General Electric Company | Method for depositing an aluminum-containing layer onto an article |
Also Published As
Publication number | Publication date |
---|---|
WO2008145093A3 (en) | 2009-04-30 |
WO2008145093A2 (en) | 2008-12-04 |
DE102007025697A1 (en) | 2008-12-04 |
EP2150631A2 (en) | 2010-02-10 |
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